CN112478154A - Rotor propeller suitable for tilt-rotor aircraft - Google Patents
Rotor propeller suitable for tilt-rotor aircraft Download PDFInfo
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- CN112478154A CN112478154A CN202011415047.6A CN202011415047A CN112478154A CN 112478154 A CN112478154 A CN 112478154A CN 202011415047 A CN202011415047 A CN 202011415047A CN 112478154 A CN112478154 A CN 112478154A
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- torsion arm
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
- B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
- B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
- B64C29/0033—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers the propellers being tiltable relative to the fuselage
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
- B64C27/14—Direct drive between power plant and rotor hub
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/52—Tilting of rotor bodily relative to fuselage
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- Aviation & Aerospace Engineering (AREA)
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Abstract
The invention provides a rotor blade suitable for a tilt rotor aircraft, comprising: the electric drive assembly is used for driving the blades to rotate at a high speed; the rotor blade control assembly is used for realizing the total pitch adjustment and the periodic pitch change of the rotor blades; the tilting assembly is used for driving the electric drive assembly and the rotor blade control assembly to rotate; the electric drive assembly with the rotor oar is controlled the subassembly and is connected, the rotor oar axle in the electric drive assembly sets up in the center of rotor oar and controls the subassembly, two the rotor oar control the subassembly set up respectively in both ends about the subassembly that verts, the chord length, the torsion angle and the wing section of paddle constantly change along the radius direction.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to a rotor blade suitable for a tilt rotor aircraft.
Background
The tilt rotor aircraft is in the two wing tip departments of similar fixed wing aircraft wing, each dress set can be at the pivoted rotor subassembly that verts between horizontal position and vertical position, when the aircraft takes off perpendicularly and lands, rotor shaft perpendicular to ground, be the horizontal formula helicopter flight state, and can hover in the air, fly around and the side, take off after reaching the certain speed at the tilt rotor aircraft, the rotor shaft can be forward or 90 jiaos of verting backward, be horizontal state, the rotor uses as pulling force screw or thrust screw, the tilt rotor can do long-range flight like fixed wing aircraft with higher speed this moment, the driving system of tilt rotor aircraft possesses the dual function of screw and rotor simultaneously promptly.
The fixed wing aircraft generally adopts propellers as a power device, the helicopter generally adopts a rotor wing as a power device, the propellers are devices which rotate in the air or water by means of blades and convert the rotating power of an engine into propulsive force, two or more blades can be connected with a hub, and the backward surface of each blade is a helicoid or a propeller similar to the helicoid; the rotor wing is an important part of the helicopter, and plays a dual role in generating lift force and pulling force in the flying process of the helicopter; the rotor is composed of a hub and a plurality of blades, the hub is arranged on a rotor shaft, the blades in the shape of slender wings are connected on the hub, but the rotor shaft of the common rotor is generally arranged along the vertical direction and cannot rotate to the horizontal direction.
Correspondingly, the tilt rotor aircraft adopts a rotor blade or a rotor blade as a power device. This patent will be applied to on the gyroplane that verts, can enough provide horizontal tension for the gyroplane that verts in order to overcome full quick-witted aerodynamic resistance and realize its high-speed flat flight, can provide vertical tension again in order to overcome earth gravitation in order to realize the gyroplane that verts VTOL and the power device definition of hovering steadily be rotor oar or oar rotor, and vertical direction can be followed to the rotor shaft of its rotor, also can rotate to the horizontal direction to distinguish with ordinary rotor.
However, for the rotor tilting machine, because it can take off and land vertically and hover in the air, and can fly at high speed, the difference between the flight speeds corresponding to the two states is large, on the other hand, the difference between the pulling forces required by the two states is also large, the pulling force of the power system in the hovering state is equal to the total weight of the aircraft, and the pulling force of the power system in the forward flying state is about one tenth of the total weight of the aircraft, a structure of a rotor paddle (paddle rotor) and a blade used for the rotor paddle (paddle rotor) need to be designed pneumatically in a targeted manner, so that the requirements of the tilting rotor machine on the power system are met.
Disclosure of Invention
In order to solve the problems, the invention provides a rotor blade (also called a rotor blade) suitable for a tilt rotor aircraft, so as to solve the problems of difficult power source arrangement, complex operating mechanism and the like of the traditional tilt rotor blade; the motor is adopted for direct drive, and a novel total pitch, longitudinal periodic pitch changing mechanism and an electric tilting mechanism are designed, so that the tilting mechanism is more suitable for small and medium-sized unmanned tilting rotorcraft, and has the advantages of simple structure, high reliability and light weight; compared with a conventional helicopter rotor system, the variable-pitch propeller disclosed by the invention can realize a larger blade pitch range, and meets the requirement of a tilt rotor aircraft on a large pitch in a forward flight axial flow state.
The invention provides a rotor blade suitable for a tiltrotor aircraft, comprising: the electric drive assembly is used for driving the blades to rotate at a high speed; the rotor blade control assembly is used for realizing the total pitch adjustment and the periodic pitch change of the rotor blades; the tilting assembly is used for driving the electric drive assembly and the rotor blade control assembly to rotate; the electric drive assembly with the rotor oar is controlled the subassembly and is connected, the rotor oar axle in the electric drive assembly sets up in the center of rotor oar and controls the subassembly, two the rotor oar control the subassembly set up respectively in both ends about the subassembly that verts, the chord length, the torsion angle and the wing section of paddle constantly change along the radius direction.
Further, the twist angle of the blade of the rotor blade is smaller than that of the blade of the propeller under the same condition, and is larger than that of the blade of the rotor.
Further, the diameter of the rotor blade is smaller than the diameter of the propeller under the same requirement condition, and is larger than the diameter of the rotor under the same condition.
Further, the angle range of the periodic variable pitch of the blades is-20 degrees.
Further, the electric drive assembly includes a motor and a rotor shaft, the rotor shaft being coupled to an output shaft of the motor.
Further, the electric drive assembly further comprises a motor speed regulator, the motor speed regulator is fixedly connected with the motor, and the motor speed regulator is used for controlling the rotation speed regulation of the motor.
Further, the rotor blade control assembly is a unidirectional pitch mechanism.
Furthermore, the rotor blade control assembly comprises a rack, a steering engine rocker arm, a second connecting rod, a lower torsion arm lever, a lower torsion arm support, a lower torsion arm connecting rod, an inclinator outer ring, an inclinator inner ring assembly, a first upper torsion arm, a second upper torsion arm, an upper torsion arm hoop, a first connecting rod, a blade clamp and a blade hub; the steering engine and the lower torque arm support are fixedly connected with the rack; the steering engine, the steering engine rocker arm, the second connecting rod and the lower torsion arm lever are sequentially connected; the lower torsion arm lever is hinged with the lower torsion arm support and the lower torsion arm connecting rod at the same time, and the lower torsion arm connecting rod is hinged with the outer ring of the inclinator; the outer side of the tilter inner ring component is hinged with the tilter outer ring, and the inner side of the tilter inner ring component is connected with the rotor shaft through a spherical hinge; the tilter inner ring assembly is connected with a rocker arm of the paddle clamp through a first connecting rod; the inclinator inner ring assembly, the first upper torsion arm, the second upper torsion arm and the upper torsion arm hoop are connected in sequence; the upper torque arm hoop is fixedly connected with the rotor shaft; the paddle clamp is hinged to the hub, and the hub is hinged to the rotor shaft.
Furthermore, the tilting assembly comprises a tilting rudder base, a tilting steering engine, an operating rod, a tilting bearing and a tilting rod which are connected in sequence; the left end and the right end of the tilting rod are respectively fixedly connected with a pipe joint, and the pipe joints are fixedly connected with a rack of the rotor blade control assembly.
Furthermore, the tilting steering engine is a linear steering engine, and the actuating stroke of the tilting steering engine can enable the rotation range of the electric drive assembly and the rotor blade control assembly to reach 0-95 degrees.
The invention has the beneficial effects that: the rotor propeller is directly driven by the motor, and a novel total pitch, longitudinal periodic pitch changing mechanism and an electric tilting mechanism are designed, so that the rotor propeller is more suitable for small and medium-sized unmanned tilting rotorcraft, and has the advantages of simple structure, high reliability and light weight; compared with a conventional helicopter rotor system, the rotor blade of the invention can realize a larger blade pitch range, and meet the power requirements of a tilt rotor aircraft for flying in two states; in the geometrical and motion characteristics, the diameter of the propeller is small, the torsion angle is large, the rotating speed is high, the diameter of the rotor is large, the torsion angle is small, and the rotating speed is low.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the provided drawings without creative efforts.
Figure 1 is a schematic view of a rotor blade assembly suitable for a tiltrotor aircraft;
FIG. 2 is a schematic structural view of a blade;
FIG. 3 is a schematic diagram of the components of the electric drive assembly;
FIG. 4 is a schematic view of a rotor blade steering assembly;
fig. 5 is a schematic view of the tilt assembly.
Description of reference numerals:
100-an electric drive assembly; 101-motor speed controller; 102-a motor; 103-a coupler; 104-rotor shaft; 200-a rotor-paddle steering assembly; 201-a frame; 202-lower torque arm support; 203-lower torsion arm lever; 204-lower torsion arm linkage; 205-a tilter inner ring assembly; 206-a first upper torsion arm; 207-a second upper torsion arm; 208-paddle clamp; 209-hub; 210-an upper torque arm yoke; 211-a first link; 212-tilter outer ring; 213-a steering engine; 214-a second link; 215-steering engine rocker arm; 300-a tilt assembly; 301-tilting the rudder mount; 302-tilt steering engine; 303-a joystick; 304-tilt bearings; 305-a tilt lever; 306-a pipe joint; 400-paddle.
Detailed Description
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in detail below. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
Referring to fig. 1, a rotor blade (also referred to as a rotor blade) for a tiltrotor aircraft includes an electric drive assembly 100, a rotor blade steering assembly 200, a tilt assembly 300, and a blade 400, wherein the electric drive assembly 100 is configured to drive the blade 400 to rotate at a high speed; rotor blade steering assembly 200 may adjust the setting angle of blades 400 for collective pitch adjustment and longitudinal cyclic pitch variation of the rotor blades; tilt assembly 300 is configured to rotate electric drive assembly 100 and rotor paddle assembly 200. Electric drive assembly 100 is coupled to a paddle steering assembly 200, and paddle steering assembly 200 is disposed at both left and right ends of tilt assembly 300.
Referring to FIG. 2, the chord length, twist angle, and airfoil profile of blade 400 vary along the radius.
The twist angle of the blade is an included angle between an airfoil chord line and a blade rotating plane, changes along with the change of the radius, and the change rule of the twist angle is the most main factor influencing the working performance of a rotor blade, a propeller and a rotor.
The paddle torsional angle of rotor oar is less than the paddle torsional angle of screw under the same condition, is greater than the paddle torsional angle of rotor simultaneously to satisfy the pulling force requirement when verting the gyroplane and hovering, transition and flying before high-speed, improve the aerodynamic efficiency of rotor oar.
The diameter of the rotor blade, the diameter of the propeller and the diameter of the rotor are all the diameters of the blade tip track circle of the blade. The diameter of rotor oar is less than the diameter of screw under the same requirement condition, is greater than the diameter of rotor under the same condition simultaneously, guarantees to vert the gyroplane and can descend at the fixed wing state, improves the aerodynamic efficiency of helicopter state as far as simultaneously.
Referring to fig. 3, the electric drive assembly 100 includes a motor governor 101, a motor 102, a coupling 103, and a rotor shaft 104; the motor speed regulator 101 is fixedly connected with the motor 102, the motor speed regulator 101 is used for controlling the rotation speed adjustment of the motor 102, and the rotor shaft 104 is connected with the motor 102 through the coupler 103 and used for transmitting the torque generated by the motor 102 to the rotor shaft 104.
Referring to fig. 4, rotor blade steering assembly 200 includes a frame 201, a lower torque arm support 202, a lower torque arm lever 203, a lower torque arm link 204, an tilter inner ring assembly 205, a first upper torque arm 206, a second upper torque arm 207, a blade clamp 208, a hub 209, an upper torque arm yoke 210, a first link 211, an tilter outer ring 212, a steering engine 213, a second link 214, and a steering engine rocker 215.
Frame 201 is used to support the other components of electric drive assembly 100 and rotor paddle assembly 200 described above. Lower torque arm support 202 is fixedly attached to frame 201 for supporting rotor shaft 104.
The number of the steering engines 213, the steering engine rocker arm 215, the second connecting rod 214 and the lower torsion arm lever 203 is two, and each steering engine 213, the steering engine rocker arm 215, the second connecting rod 214 and the lower torsion arm lever 203 are connected in sequence; the two lower torque arm levers 203 are respectively hinged with two ends of the lower torque arm support 202; the steering engine 213 is fixedly connected with the frame 201 and can drive a steering engine rocker arm 215 to rotate, the steering engine rocker arm 215 is connected with one end of a second connecting rod 214 through a joint bearing, and the other end of the second connecting rod 214 is connected with the lower torsion arm lever 203 through a joint bearing; one end of the lower torsion arm connecting rod 204 is hinged with the lower torsion arm lever 203, and the other end is hinged with the tilter outer ring 212; the outer side of tilter inner ring assembly 205 is hinged to tilter outer ring 212, and the inner side is connected to rotor shaft 104 by a spherical hinge; first upper torsion arm 206 is connected to tilter inner ring assembly 205 via a knuckle bearing; one end of the second upper torque arm 207 is hinged to the first upper torque arm 206 and the other end is hinged to an upper torque arm clip 210, the upper torque arm clip 210 being fixedly connected to the rotor shaft 104; the paddle clamp 208 is hinged with a paddle hub 209 and is used for mounting the blades of the rotor paddle; hub 209 is hinged to rotor shaft 104, and hub 209 and rotor shaft 104 have a rotational degree of freedom therebetween to accommodate blade flapping; first link 211 has one end coupled to the swing arm of paddle clamp 208 via a knuckle bearing and the other end coupled to tilter inner ring assembly 205 via a knuckle bearing.
The connection between lower torque arm support 202, lower torque arm lever 203, lower torque arm link 204, and tilter outer ring 212 are all hinged, thereby limiting the cyclic pitch of rotor assembly 200 to only a longitudinal direction.
The components in rotor blade steering assembly 200 are designed in coordination to meet the cyclic pitch angle of the blades in the range of-20 to 20.
Referring to fig. 5, tilt assembly 300 includes tilt rudder mount 301, tilt rudder 302, operating lever 303, tilt bearing 304, tilt lever 305 and pipe joint 306. The tilting rudder base 301 is fixedly connected with the aircraft body to be used as a support for the tilting assembly to actuate; one end of the tilting steering engine 302 is hinged with the tilting steering engine seat 301, the other end of the tilting steering engine 302 is hinged with the operating rod 303, and the operating rod 303 is fixedly connected with the tilting rod 305; the inner ring of the tilting bearing 304 is fixedly connected with the tilting rod 305, and the outer ring of the tilting bearing 304 is fixedly connected with the aircraft body; tilt rod 305 is fixedly attached at both ends to coupling 306, and coupling 306 is fixedly attached to frame 201 of rotor blade steering assembly 200.
The tilting steering engine 302 is a linear steering engine, and the actuating stroke of the tilting steering engine can enable the rotating range of the electric drive assembly 100 and the rotor blade control assembly 200 to reach 0-95 degrees.
Referring to fig. 3 to 5, the specific operation process of this embodiment is as follows:
referring to fig. 3 and 4, after the motor governor 101 is powered on, the driving motor 102 rotates, the shaft coupler 103 drives the rotor shaft 104 to rotate, and the rotor shaft 104 drives the hub 209 and the blade clamp 208 hinged thereto to rotate, so as to drive the blades to rotate and generate lift force. Rotor shaft 104 drives upper torque arm yoke 210 to rotate, and first upper torque arm 206 and second upper torque arm 207 hinged to it drive tilter inner ring assembly 205 and rotor shaft 104 to rotate at a constant speed, and tilter inner ring assembly 205 and rotor shaft 104 are connected in a spherical hinge manner, so that tilter inner ring assembly 205 can rotate with rotor shaft 104 while realizing a certain angle of tilt to meet the requirement of periodic variable pitch.
Referring to fig. 3, two steering engines 213 rotate two steering engine rocker arms 215 at the same or different angles, and the steering engine rocker arms 215 drive the second connecting rods 214, the lower torsion arm levers 203, the lower torsion arm connecting rods 204, the tilter inner ring assembly 205, the first upper torsion arms 206, the second upper torsion arms 207, the paddle clamps 208, the first connecting rods 211, the tilter outer rings 212 and the first connecting rods 211 to move, so that the paddle clamps 208 finally rotate around the paddle hubs 209, thereby realizing the total pitch adjustment and the longitudinal cyclic pitch change of the rotor paddles.
Referring to fig. 5, the tilt actuator 302 actuates and pushes or pulls the operating rod 303 to rotate the tilt rod 305 around the tilt bearing 304, and the pipe joint 306 fixedly connected to the tilt rod 305 drives the frame 201 to rotate, thereby driving the electric drive assembly 100 and the rotor blade control assembly 200 to rotate around the tilt bearing 304.
When the tilt rotor aircraft flies horizontally at a high speed, the integral structure consisting of the electric drive assembly 100, the rotor blade control assembly 200 and the blades 400 is driven by the tilt assembly 300 to rotate around the axis of the tilt rod 305, so that the rotor blade shaft 104 is parallel to the flight direction, and the pulling force provided by the rotor blades in the state is equal to the aerodynamic resistance of the whole aircraft;
when the tilt-rotor aircraft is hovering stably or vertically ascends and descends stably, the whole structure formed by the electric drive assembly 100, the rotor paddle control assembly 200 and the blades 400 is driven by the tilt assembly 300 to rotate around the axis of the tilt rod 305, so that the rotor paddle shaft 104 is approximately in the vertical direction, and the pulling force provided by the rotor paddle in the state is equal to the gravity of the whole aircraft.
The invention has the beneficial effects that: the rotor propeller is directly driven by the motor, and a novel total pitch, longitudinal periodic pitch changing mechanism and an electric tilting mechanism are designed, so that the rotor propeller is more suitable for small and medium-sized unmanned tilting rotorcraft, and has the advantages of simple structure, high reliability and light weight; compared with a conventional helicopter rotor system, the rotor blade of the invention can realize a larger blade pitch range, and meet the power requirements of a tilt rotor aircraft for flying in two states; in the geometrical and motion characteristics, the diameter of the propeller is small, the torsion angle is large, the rotating speed is high, the diameter of the rotor is large, the torsion angle is small, and the rotating speed is low.
Finally, it should also be noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element.
The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (10)
1. A rotor-paddle suitable for a tiltrotor aircraft, comprising: the electric drive assembly (100) is used for driving the paddle (400) to rotate at a high speed; the rotor blade control assembly (200) is used for realizing the total pitch adjustment and the periodic pitch change of the rotor blades; the tilting assembly (300) is used for driving the electric drive assembly (100) and the rotor blade control assembly (200) to rotate; electric drive assembly (100) with rotor oar is controlled subassembly (200) and is connected, rotor oar axle (104) in electric drive assembly (100) sets up in the center that rotor oar was controlled subassembly (200), two rotor oar is controlled subassembly (200) set up respectively in both ends about tilting subassembly (300), the chord length, the torsion angle and the wing section of paddle (400) constantly change along the direction of radius.
2. A rotor blade adapted for use in a tiltrotor aircraft according to claim 1, wherein the twist angle of the blade of the rotor blade is less than the twist angle of the blade of the rotor under the same conditions, and greater than the twist angle of the blade of the rotor.
3. A rotor blade adapted for use in a tiltrotor aircraft according to claim 1, wherein the rotor blade has a diameter that is less than the diameter of the rotor under the same requirements and greater than the diameter of the rotor under the same requirements.
4. A rotor blade suitable for a tiltrotor aircraft according to claim 1, wherein the cyclic pitch of the blade (400) is in the range of-20 ° -20 °.
5. A rotor blade suitable for use in a tiltrotor aircraft according to claim 1, wherein the electrical drive assembly (100) comprises an electrical motor (102) and a rotor shaft (104), the rotor shaft (104) being coupled to an output shaft of the electrical motor (102).
6. Rotor paddle suitable for a tiltrotor aircraft according to claim 5, wherein the electric drive assembly (100) further comprises a motor governor (101), the motor governor (101) being fixedly connected to the motor (102), the motor governor (101) being adapted to control the speed adjustment of the motor (102).
7. A rotor blade adapted for a tiltrotor aircraft according to claim 1, wherein said rotor blade steering assembly (200) is a unidirectional pitch mechanism.
8. The rotor blade suitable for a tiltrotor aircraft according to claim 6, wherein the rotor blade steering assembly (200) comprises a frame (201), a steering engine (213), a steering engine rocker arm (215), a second link (214), a lower torsion arm lever (203), a lower torsion arm mount (202), a lower torsion arm link (204), a tilter outer ring (212), a tilter inner ring assembly (205), a first upper torsion arm (206), a second upper torsion arm (207), an upper torsion arm yoke (210), a first link (211), a blade clamp (208), and a hub (209); the steering engine (213) and the lower torsion arm support (202) are fixedly connected with the rack (201); the steering engine (213), the steering engine rocker arm (215), the second connecting rod (214) and the lower torsion arm lever (203) are connected in sequence; the lower torsion arm lever (203) is hinged with the lower torsion arm support (202) and the lower torsion arm connecting rod (204) at the same time, and the lower torsion arm connecting rod (204) is hinged with the outer ring (212) of the tilter; the outer side of the tilter inner ring assembly (205) is hinged with a tilter outer ring (212), and the inner side of the tilter inner ring assembly is connected with the rotor shaft (104) through a spherical hinge; the connection of the tilter inner ring assembly (205) to the swing arm of the paddle clamp (208) via a first link (211); the recliner inner ring assembly (205), the first upper torsion arm (206), the second upper torsion arm (207) and the upper torsion arm hoop (210) are connected in sequence; the upper torque arm clamp (210) is fixedly connected with the rotor shaft (104); the paddle clamp (208) is hinged to a hub (209), and the hub (209) is hinged to the rotor shaft (104).
9. The rotor blade suitable for a tiltrotor aircraft according to claim 1, wherein the tilt assembly (300) comprises a tilt rudder machine base (301), a tilt steering machine (302), an operating lever (303), a tilt bearing (304) and a tilt lever (305) which are connected in sequence; the left end and the right end of the tilting rod (305) are respectively fixedly connected with a pipe joint (306), and the pipe joints (306) are fixedly connected with a frame (201) of the rotor blade control assembly (200).
10. The rotor blade for a tiltrotor aircraft according to claim 9, wherein the tilt actuator (302) is a linear actuator having an actuation stroke that allows the electric drive assembly (100) and the rotor blade control assembly (200) to rotate in a range of 0 ° to 95 °.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011415047.6A CN112478154B (en) | 2020-12-05 | 2020-12-05 | Rotor propeller suitable for tilt-rotor aircraft |
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| CN202011415047.6A CN112478154B (en) | 2020-12-05 | 2020-12-05 | Rotor propeller suitable for tilt-rotor aircraft |
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| CN116062163A (en) * | 2023-02-10 | 2023-05-05 | 南京航空航天大学 | Rotor craft and become burden and turn round paddle thereof |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113942640A (en) * | 2021-10-09 | 2022-01-18 | 中国直升机设计研究所 | Interior control rotor support piece structure |
| CN113942640B (en) * | 2021-10-09 | 2023-04-28 | 中国直升机设计研究所 | Inner control rotor wing supporting piece structure |
| CN116062163A (en) * | 2023-02-10 | 2023-05-05 | 南京航空航天大学 | Rotor craft and become burden and turn round paddle thereof |
| CN116062163B (en) * | 2023-02-10 | 2024-03-12 | 南京航空航天大学 | Rotor craft and become burden and turn round paddle thereof |
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| CN112478154B (en) | 2022-04-12 |
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